DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Reynolds number: 50,000 Max Cl/Cd: 28.27 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-defcnd2-il-50000-n5.txt Download as CSV file: xf-defcnd2-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DEFIANT CANARD BL110 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3083 0.10200 0.09558 -0.0497 1.0000 0.0577
-9.500 -0.3164 0.09915 0.09285 -0.0492 1.0000 0.0568
-9.250 -0.3287 0.09650 0.09033 -0.0482 1.0000 0.0559
-9.000 -0.3451 0.09404 0.08800 -0.0468 1.0000 0.0550
-8.750 -0.3653 0.09155 0.08563 -0.0454 1.0000 0.0542
-8.500 -0.3899 0.08876 0.08296 -0.0444 1.0000 0.0534
-8.250 -0.4130 0.08400 0.07827 -0.0472 0.9957 0.0521
-8.000 -0.4458 0.07453 0.06837 -0.0554 0.9785 0.0491
-7.750 -0.4382 0.06983 0.06350 -0.0582 0.9694 0.0488
-7.500 -0.4345 0.06568 0.05914 -0.0595 0.9591 0.0486
-7.250 -0.4287 0.06146 0.05460 -0.0606 0.9496 0.0485
-7.000 -0.4192 0.05728 0.04998 -0.0617 0.9408 0.0489
-6.750 -0.4112 0.05387 0.04621 -0.0613 0.9309 0.0496
-6.500 -0.3864 0.05123 0.04346 -0.0630 0.9246 0.0514
-6.250 -0.3737 0.04876 0.04070 -0.0621 0.9147 0.0524
-6.000 -0.3494 0.04563 0.03709 -0.0631 0.9082 0.0532
-5.500 -0.3039 0.04057 0.03115 -0.0628 0.8921 0.0550
-5.250 -0.2810 0.03864 0.02880 -0.0622 0.8828 0.0566
-5.000 -0.2463 0.03667 0.02624 -0.0632 0.8764 0.0603
-4.750 -0.2194 0.03511 0.02462 -0.0633 0.8671 0.0634
-4.500 -0.1853 0.03361 0.02294 -0.0641 0.8593 0.0670
-4.250 -0.1504 0.03226 0.02131 -0.0647 0.8507 0.0718
-4.000 -0.1207 0.03116 0.02020 -0.0647 0.8408 0.0798
-3.750 -0.0828 0.02986 0.01878 -0.0660 0.8332 0.0915
-3.500 -0.0588 0.02892 0.01782 -0.0650 0.8213 0.1087
-3.250 -0.0335 0.02777 0.01682 -0.0645 0.8102 0.1473
-3.000 -0.0087 0.02594 0.01576 -0.0642 0.8016 0.2657
-2.750 -0.0045 0.02439 0.01563 -0.0595 0.7890 0.5060
-2.500 0.0209 0.02418 0.01604 -0.0559 0.7785 0.7495
-2.250 0.0829 0.02451 0.01612 -0.0584 0.7723 0.8580
-2.000 0.1681 0.02498 0.01611 -0.0667 0.7642 0.9140
-1.750 0.2553 0.02490 0.01553 -0.0765 0.7572 0.9513
-1.500 0.3151 0.02467 0.01498 -0.0828 0.7456 0.9725
-1.250 0.3644 0.02435 0.01439 -0.0873 0.7340 0.9874
-1.000 0.4102 0.02399 0.01376 -0.0913 0.7227 0.9995
-0.750 0.4279 0.02389 0.01350 -0.0899 0.7109 1.0000
-0.500 0.4409 0.02392 0.01340 -0.0878 0.6980 1.0000
-0.250 0.4544 0.02395 0.01331 -0.0858 0.6856 1.0000
0.000 0.4690 0.02397 0.01320 -0.0838 0.6742 1.0000
0.250 0.4868 0.02390 0.01298 -0.0822 0.6645 1.0000
0.500 0.5010 0.02398 0.01294 -0.0801 0.6533 1.0000
0.750 0.5146 0.02412 0.01297 -0.0780 0.6423 1.0000
1.000 0.5321 0.02417 0.01288 -0.0763 0.6329 1.0000
1.250 0.5491 0.02427 0.01285 -0.0745 0.6231 1.0000
1.500 0.5632 0.02451 0.01299 -0.0724 0.6127 1.0000
1.750 0.5831 0.02459 0.01293 -0.0710 0.6039 1.0000
2.000 0.5995 0.02484 0.01308 -0.0691 0.5943 1.0000
2.250 0.6161 0.02515 0.01329 -0.0674 0.5852 1.0000
2.500 0.6380 0.02533 0.01335 -0.0664 0.5776 1.0000
2.750 0.6528 0.02579 0.01375 -0.0644 0.5685 1.0000
3.000 0.6781 0.02589 0.01370 -0.0638 0.5614 1.0000
3.250 0.6911 0.02642 0.01421 -0.0616 0.5515 1.0000
3.500 0.7128 0.02666 0.01434 -0.0605 0.5434 1.0000
3.750 0.7305 0.02705 0.01466 -0.0589 0.5343 1.0000
4.000 0.7482 0.02748 0.01504 -0.0573 0.5261 1.0000
4.250 0.7682 0.02787 0.01538 -0.0561 0.5184 1.0000
4.500 0.7857 0.02842 0.01591 -0.0546 0.5115 1.0000
4.750 0.8020 0.02905 0.01655 -0.0531 0.5047 1.0000
5.000 0.8293 0.02934 0.01679 -0.0529 0.5000 1.0000
5.250 0.8351 0.03041 0.01796 -0.0501 0.4928 1.0000
5.500 0.8563 0.03093 0.01848 -0.0493 0.4874 1.0000
5.750 0.8735 0.03164 0.01921 -0.0479 0.4819 1.0000
6.000 0.8828 0.03264 0.02029 -0.0457 0.4755 1.0000
6.250 0.9079 0.03303 0.02071 -0.0453 0.4708 1.0000
6.500 0.9130 0.03427 0.02205 -0.0426 0.4646 1.0000
6.750 0.9252 0.03522 0.02308 -0.0408 0.4590 1.0000
7.000 0.9525 0.03560 0.02347 -0.0408 0.4552 1.0000
7.250 0.9438 0.03754 0.02558 -0.0369 0.4488 1.0000
7.500 0.9535 0.03872 0.02684 -0.0350 0.4438 1.0000
7.750 0.9812 0.03913 0.02730 -0.0350 0.4404 1.0000
8.000 0.9475 0.04234 0.03063 -0.0288 0.4332 1.0000
8.250 0.9530 0.04389 0.03226 -0.0269 0.4284 1.0000
8.500 0.9827 0.04420 0.03265 -0.0271 0.4255 1.0000
8.750 0.9148 0.05092 0.03943 -0.0213 0.4147 1.0000
9.000 0.9402 0.05127 0.03990 -0.0209 0.4117 1.0000
9.500 0.8978 0.06076 0.04949 -0.0184 0.3969 1.0000
10.250 0.8220 0.07974 0.06862 -0.0195 0.3741 1.0000
10.500 0.8265 0.08261 0.07156 -0.0195 0.3700 1.0000
10.750 0.8473 0.08347 0.07257 -0.0190 0.3672 1.0000
11.000 0.8220 0.08960 0.07873 -0.0198 0.3586 1.0000
11.250 0.8362 0.09112 0.08036 -0.0195 0.3540 1.0000
11.500 0.8630 0.09121 0.08059 -0.0188 0.3512 1.0000
11.750 0.8338 0.09779 0.08721 -0.0199 0.3414 1.0000
12.000 0.8550 0.09848 0.08804 -0.0194 0.3373 1.0000
12.250 0.8421 0.10310 0.09276 -0.0201 0.3288 1.0000
12.500 0.8579 0.10428 0.09406 -0.0197 0.3231 1.0000
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